GH4169镍基高温合金超高频振动疲劳实验  

Experimental on ultrahigh frequency vibration fatigue of GH4169 nickel-based superalloy

作　　者：王昭晗 潘凯 陈永辉[1] 杭超 王永杰 燕群[1] WANG Zhaohan;PAN Kai;CHEN Yonghui;HANG Chao;WANG Yongjie;YAN Qun(National Key Laboratory of Strength and Structural Integrity,Aircraft Strength Research Institute of China,Xi’an 710000,China;Chinese Aeronautical Establishment,Beijing 100020,China;School of Mechanical and Power Engineering,East China University of Science&Technology,Shanghai 200237,China)

机构地区：[1]中国飞机强度研究所强度与结构完整性全国重点实验室,西安710000 [2]中国航空研究院,北京100020 [3]华东理工大学机械与动力工程学院,上海200237

出　　处：《航空材料学报》2025年第2期110-118,共9页Journal of Aeronautical Materials

基　　金：国家科技重大专项(J2019-Ⅳ-0010-0078)。

摘　　要：为解决航空发动机常用GH4169镍基高温合金超高周疲劳问题,基于压电超声疲劳测试系统,设计出一种可实现20 kHz超高频振动疲劳试样并完成测试;获得常温环境下GH4169镍基高温合金在不同存活概率5%、50%及95%下超高周振动疲劳P-S-N曲线。测试结果表明:GH4169材料的疲劳寿命在达到10^(7)周次后曲线呈下降趋势,没有出现疲劳极限,试样仍发生疲劳破坏。断口分析表明:超高周疲劳裂纹大多起源于试样表面或亚表面的位置,存在单点起裂和多源起裂的情况,起裂方式表现为表面滑移起裂与非金属夹杂物滑移起裂两种形式。To address the very high cycle fatigue(VHCF)issue of GH4169 nickel-based superalloy,which is widely utilized in aeroengines,a fatigue specimen subjected to 20 kHz ultrahigh frequency vibration is designed and tested utilizing a piezoelectric ultrasonic fatigue testing system.At room temperature,the P-S-N curves for VHCF of GH4169 nickel-based superalloy are obtained under various survival probabilities of 5%,50%,and 95%.The experimental findings reveal that the GH4169 material’s curve exhibits a downward trend when the fatigue life attains 10^(7) cycles,indicating the absence of a fatigue limit and the persistence of fatigue failure.Fracture analysis results indicate that the majority of VHCF cracks initiate from the surface or subsurface of the specimen,with both single-source and multi-source cracking observed.The cracking modes encompass surface sliding cracking and non-metallic inclusion-induced sliding cracking.

关 键 词：航空发动机 镍基高温合金 超高频振动 超高周疲劳 P-S-N曲线 

分 类 号：V250.2[一般工业技术—材料科学与工程]